Propeller pitch lock system

ABSTRACT

A variable pitch propulsor system with a propeller pitchlock system which utilizes a follower style pitchlock ballscrew screw which tracks the actuator axial stroke. The pitchlock system transfers the propeller yoke loads, from the ballscrew ballnut to the pitchlock nut allowing the propeller to pitchlock; utilizes the same screw thread lead angle for normal ballscrew back driving operation as well as pitch locking capabilities; provides a single ballscrew which is capable of both being back driven by the ballnut and structurally adequate for reacting the blade loads resulting from any flight condition; and minimizes the requirement of additional rotation and torque transferring interfaces between the ballscrew and pitchlock nut.

BACKGROUND OF THE INVENTION

The present invention relates to propulsor systems, and more particularly to a pitchlocking system which utilizes a common ballscrew for operation with a ballscrew ballnut and a pitchlock screw nut thereby requiring fewer parts and less axial space.

In typical variable pitch propulsor systems, a plurality of propulsor blades, each pivotably mounted for movement about its longitudinal axis relative to a rotary hub driven by an aircraft engine, are operatively connected to a mechanical or hydromechanical blade pitch change system disposed within the hub assembly. Pitch change systems typically include a pitchlock for maintaining blade pitch in the event of a malfunction such as a loss in the system's hydraulic supply.

Conventional pitch lock systems often incorporate a pitch lock screw to provide a locking mechanism which prevents the blades from moving to a lower blade angle in addition to a separate ballscrew mechanism which is backdriven to rotationally drive the pitchlock screw. Although effective, such conventional arrangements are relatively complicated and require a relatively significant axial envelope within the hub assembly to mount both the ballscrew and pitchlock screw.

Accordingly, it is desirable to provide a variable pitch propulsor system with an uncomplicated and lightweight pitchlocking system having a minimal axial envelope.

SUMMARY OF THE INVENTION

A variable pitch propulsor system according to the present invention provides a pitchlocking system in which the propeller blade loads, (ie. twisting moments), are transmitted about a blade centerline, through a blade pin and reacted by a yoke assembly as an axial load. The yoke assembly includes an actuator piston which is hydraulically capable of outputting a force which overcomes the blade loads and position the blades to a desired pitch angle.

The pitchlocking system locks the propeller actuator at an axial location which corresponds to a current blade pitch angle should the actuator piston no longer react the loads from the blades. The pitchlock system locks the actuator and prevents a decrease in blade angle when the resulting aerodynamic blade loads are in the fine pitch direction.

The propeller pitchlock system utilizes a “follower” style pitchlock ballscrew screw which tracks the actuator's axial stroke. The axial movement of a ballscrew ballnut, which is fixed to the actuator yoke, is converted to rotational motion through ball bearings riding in a balltrack at a pre-selected helix angle to back drive the ballscrew. The ballscrew rotationally advances or retreats relative to the ballnut and maintains a constant pitchlock gap for all actuator yoke axial positions, (ie. blade angles).

Should a hydraulic condition occur where the coarse pitch pressure cannot support the blade loads, a pitchlock piston strokes to reposition the ballscrew ground such that the ballscrew closes the pitchlock gap. When the pitchlock gap is closed, there is contact between the ballscrew and the actuator dome cover. The screw then rotationally locks due to the thread lead angle, ballscrew flange end configuration and spring force on the pitchlock piston connection. The aerodynamic forces on the blades continue to axially load the ballnut through the yoke assembly in the fine pitch direction until the load exceeds the spring force of the springs which axially position the ballnut in the yoke bore. The ballnut then slides in the yoke bore until the pitchlock nut threads contact the ballscrew's ball tracks and transfers the blade loads to a pitchlock nut.

The pitch lock nut screw thread lead angle is selected such that when the blade loads are transferred to the pitchlock nut threads, the loads cannot back drive the ballscrew in the pitchlock nut which then holds the yoke/actuator and blades in a fixed pitch position. The propeller system is then pitchlocked and operates at that fixed pitch position.

The present invention thereby transfers the propeller yoke loads, (ie. blade loads), from the ballnut to the pitchlock nut allowing the propeller to pitchlock; utilizes the same screw thread lead angle for normal ballscrew back driving operation as well as pitch locking capabilities; provides a single ballscrew which is both back driven by the ballnut and structurally adequate for reacting the blade loads resulting from any flight condition and actuator output; and minimizes the requirement of additional rotation and torque transferring interfaces between the ballscrew and pitchlock nut.

The present invention therefore provides a variable pitch propulsor system with an uncomplicated and light weight pitchlocking system within a minimal axial envelope.

BRIEF DESCRIPTION OF THE DRAWINGS

The various features and advantages of this invention will become apparent to those skilled in the art from the following detailed description of the currently preferred embodiment. The drawings that accompany the detailed description can be briefly described as follows:

FIG. 1 is a general perspective view an exemplary gas turbine turboprop engine embodiment for use with the present invention;

FIG. 2A is a sectional view of a turboprop system illustrating the electronic/hydraulic control system along a hub axis of rotation;

FIG. 2B is an expanded partial sectional view of a pitch change system valve illustrated in FIG. 2A;

FIG. 3 is an expanded view of a ballscrew, ballscrew ballnut, and pitchlock nut in a pitchlock condition;

FIG. 4A is an expanded sectional view of the pitchlock system in a normal operating position;

FIG. 4B is an expanded sectional view of the pitchlock system in a first initiated position;

FIG. 4C is an expanded sectional view of the pitchlock system in a second initial pitchlock load reaction position; and

FIG. 4D is an expanded sectional view of the pitchlock system in a peak pitchlock load reaction position.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT

FIG. 1 illustrates a general perspective view of a propeller system 20 driven by a gas turbine engine (illustrated schematically at 22). The engine 22 rotates a turbine output shaft 24 at a high speed to drives a gear reduction gearbox (illustrated somewhat schematically at 26) which decrease shaft rotation speed and increase output torque. The gearbox 26 drives a propeller shaft 28 which rotates a hub assembly 30 and a plurality of propeller blades 32 which extend therefrom. The hub axis A is substantially perpendicular to a plane P which is defined by the propeller blades 32.

Referring to FIG. 2A, a sectional view of the propeller system 20 is illustrated. A main pump 36, for actuating the various mechanism disclosed herein, provides hydraulic pressure. The main pump 36 provides a pressure indicated generally by the appropriately shaded areas and more specifically by the P_(subscript) designations, wherein P_(c) is coarse pitch pressure, P_(F) is fine pitch pressure, and P_(PL) is pitchlock pressure.

The main pump 36 provides fluid pressure to the transfer bearing 38 through a electronically controlled servo valve 42. A feathering solenoid 44 and a high pressure relief valve 45 are also preferably located between the main pump 36 and the transfer bearing 38. The pitchlock solenoid 43 is located in communication with the pitchlock pressure P_(PL) line.

From the transfer bearing 38, pitchlock pressure P_(PL) is communicated to a pitchlock system 46, while the coarse pitch pressure P_(c) and the fine pitch pressure P_(F) are supplied to a pitch change system 48 having a pitch change actuator 53. The pitch change actuator 53 is preferably mounted along the hub axis A forward of a yoke assembly 50. Generally, by selectively communicating coarse pitch pressure P_(c) and fine pitch pressure P_(F) to the pitch change system 48, speed governing, synchrophasing, beta control, feathering and unfeathering of the propeller blades 32 is hydraulically provided.

Preferably, a pitch change actuator piston 49 is located between a coarse pitch actuator chamber PC and a fine pitch actuator chamber PF defined within the pitch change actuator 53. The chambers PC, PF are respectively supplied with coarse pitch pressure P_(c) and fine pitch pressure P_(F) from a coarse pitch pressure communication circuit PC_(c) and fine pitch pressure communication circuit PF_(C) (illustrated somewhat schematically) such that the pitch change actuator piston 49 is selectively driven by differential pressure therebetween. It should be understood that the hydraulic pressure system disclose herein is illustrated somewhat schematically as various pressure communication circuits may be utilized with the present invention.

The pitch change actuator piston 49 translates along axis A to drive a yoke assembly 50. The yoke assembly 50 is attached to a pitch trunnion pin 51 which extends from each propeller blade 32 to control the pitch thereof. The yoke assembly 50 interfaces with the trunnion pin 51 at a pivot axis P which is offset from a blade axis B about which each propeller blades pitches.

The pitchlock system 46 interacts with the pitch change system 48 in response to differential pressure between pitchlock pressure P_(PL) and coarse pitch pressure P_(c). The pitchlock system 46 generally includes a pitchlock piston 52, a pitchlock ballscrew screw 54, a pitchlock nut 56, ballscrew ballnut 58 located generally along the hub axis A from forward to aft relative an aerodynamic dome assembly 60 which forms a portion of the hub assembly 30.

A ballscrew bearing support assembly 62 is mounted to a pitchlock piston load tube 63 about a pitchlock transfer tube 65 which communicates the pitchlock pressure P_(PL) to the pitchlock piston 52. The pitchlock piston 52 is located to separate a pitchlock piston coarse pitch pressure chamber 52C from a pitchlock piston pitchlock pressure chamber 52P. The pitchlock piston coarse pitch pressure chamber 52C is supplied with coarse pitch pressure P_(c) from the coarse pitch pressure communication circuit PC_(c) and the pitchlock piston pitchlock pressure chamber 52P is supplied with pitchlock pressure P_(PL) from the pitchlock pressure communication circuit PPL_(c). The pitchlock pressure P_(PL) is at least equivalent to the coarse pitch pressure P_(c) to generally balance the pitchlock piston 52 therebetween. It should be understood that the pitchlock pressure P_(PL) may be greater than the coarse pitch pressure P_(c) by a predetermined amount such that the pitchlock piston 52 is actuated in response to a predetermined difference therebetween.

The pitchlock ballscrew screw 54 is back driven within the ballscrew ballnut 58 under normal operating conditions. The pitchlock ballscrew screw 54 rotationally translates relative to the ballscrew ballnut 58. The pitchlock ballscrew screw 54 includes a continuous ballscrew ball track groove 64 with a helix angle that matches the helix angle of the pitchlock nut 56, and the ballscrew ballnut 58. The ballscrew screw 54 is mounted within the pitchlock nut 56 and the ballscrew ballnut 58 to rotationally axially advance or retreat over the full travel of the actuator yoke assembly 50.

A ballscrew screw flange 66 is located at a forward end segment of the pitchlock ballscrew screw 54. The ballscrew screw flange 66 is spaced away from an axially fixed actuator dome cover 68 during normal operation by a pitchlock gap. Should a hydraulic pressure failure occur, the pitchlock gap is closed when the ballscrew screw flange 66 contacts the actuator dome cover 68 to lock the propeller blades 32 in their last pitch position. The ballscrew screw flange 66 is capable of reacting the full actuator fine pitch hydraulic pressure output and resulting blade load under failure conditions.

Opposite the ballscrew screw flange 66, an aft end segment 67 of the pitchlock ballscrew screw 54 is mounted within the ballscrew bearing support assembly 62. The ballscrew bearing support assembly 62 is mounted to the pitchlock piston load tube 63. The ballscrew bearing support assembly 62 moves axially with the pitchlock piston load tube 63 and provides a ground relative to which the pitchlock ballscrew screw 54 rotates. That is, the pitchlock ballscrew screw 54 rotates within the ballscrew bearing support assembly 62 and the ballscrew bearing support assembly 62 is axially translatable with the pitchlock piston load tube 63 in response to actuation of the pitchlock piston 52 that supports the pitchlock piston load tube 63.

The ballscrew ballnut 58 mates with the pitchlock ballscrew screw 54. The ballscrew ballnut 58 includes a continuous mating ballnut ball track groove 72 with a helix angle equivalent to that of the ballscrew ball track groove 64. The ballnut ball track groove 72 provides the other half of the ball track for the supporting ball bearings 74. The ballscrew ballnut 58 provides both the contact surface for the ball bearings 74 as well as ball bearing containment and ball bearing crossovers.

The ballscrew ballnut 58, during normal operation, is mounted within an actuator yoke bore 76 and axially translates with the yoke assembly 50 until the ballscrew screw flange 66 contacts the axially fixed actuator dome cover 68 in response to some pitchlock input signal. At this point, when the actuator yoke 50 loads exceed a biasing force provided by a ballscrew ballnut spring 78, the ballscrew ballnut 58 will axially slide within the actuator yoke bore 76 until pitchlock nut threads 86 of the pitchlock nut 56 contact the ballscrew ball track groove 64 to pitchlock the pitchlock ballscrew screw 54 and react the aerodynamic blade loads.

The pitchlock nut 56 defines an external mounting thread 80 which corresponds to an internal thread 82 of the actuator yoke bore 76. The pitchlock nut 56 preferably includes a shoulder flange 84 which positions the pitchlock nut 56 relative the actuator yoke assembly 50. It should be understood that other attachments such as bolts or the like may alternatively be utilized.

The pitchlock nut 56 includes internal pitchlock nut threads 86 that preferably provides a toroidal profile (FIG. 3) with the same helix angle as the ballscrew ball track groove 64 such that the pitchlock nut threads 86 mate therewith. The toroidal profile of the pitchlock nut threads 86 provide a clearance relative to the ballscrew ball track groove 64 (FIG. 3) such that under normal propeller operation the ballscrew ball track groove 64 and the pitchlock nut threads 86 do not contact. When the propeller is commanded to pitchlock and the resulting blade loads are transferred through the pitchlock nut 56 into the pitchlock ballscrew screw 54, the lead angle is configured such that the pitchlock ballscrew screw 54 cannot back drive in the pitchlock nut 56 and the propeller pitchlocks.

The ball bearings 74 provide the dynamic interface between the ballscrew ballnut 58 and the pitchlock ballscrew screw 54. The ball bearings 74 travel in the mating ball grooves of the ballscrew ball track groove 64 and the ballnut ball track groove 72 when the ballscrew ballnut 58 and pitchlock ballscrew screw 54 move relative to each other. The circuit of ball bearings 74 may be diverted within ball track cross-overs located in the ballscrew ballnut 58. The cross-overs provide recirculation and unrestricted travel of the ballscrew ballnut 58 relative to the pitchlock ballscrew screw 54. Because the ball bearings 74 roll in the ballscrew ball track groove 64 and the ballnut ball track groove 72, the friction losses are minimized allowing the pitchlock ballscrew screw 54 to be backdriven within the ballscrew ballnut 58.

A timing keyway 88 is located in both the pitchlock nut 56 and the ballscrew ballnut 58 within which a lock 91 fits. Because the ballscrew ballnut 58 and pitchlock nut 56 fit about the common pitchlock ballscrew screw 54, the threads must be properly timed. The timing keyway 88 times the ballnut ball track groove 72 and the pitchlock nut threads 86. The timing keyway 88 also provides an anti-rotation feature for the ballscrew ballnut 58. That is, to impart the resulting rotational load on the pitchlock ballscrew screw 54, the ballscrew ballnut 58 itself must be rotationally held to ground.

The ballscrew ballnut spring 78 provides an axial preload on the ballscrew ballnut 58 relative to the pitchlock nut 56 to ensure that under normal operating conditions, the pitchlock ballscrew screw 54 operates through the ball bearings 74. When the propeller is commanded to pitchlock and the resulting blade loads acting through the actuator yoke assembly 50 against the pitchlock ballscrew screw 54 exceed the ballscrew ballnut spring 78, the ballscrew ballnut spring 78 begins to collapse which permits the ballscrew ballnut 58 to translate (FIGS. 4A-4D) axially along the hub axis A and transfer the loads to the pitchlock nut threads 86.

The pitchlock nut threads 86 are designed to accept high axial loads through the tangential ball track groove flanks with a radial ball bearing seat for normal ballscrew screw 54 operation. The thread profile of the pitchlock nut threads 86 preferably resemble that of an ACME thread which provides a large bearing surface and a non-back driving interface. The thread profile of the pitchlock nut threads 86 are configured such that ball bearings 74 only contact on the radial ball bearing seat of the continuous ballscrew ball track groove 64, while the ACME style pitchlock nut threads 86 only contact on the flanks of the continuous ballscrew ball track groove 64 such that minimal deleterious effect to the track groove and normal ball bearing movement results.

Referring to FIG. 4A, the pitchlock system 46 is illustrated in a normal operational position in which the pitchlock gap is maintained and differential pressure between the coarse pitch pressure P_(c) and the fine pitch pressure P_(F) operate to effectuate movement of the pitch change actuator piston 49 and resulting pitch change to the propeller blades 32 (FIG. 2A).

The pitchlock pressure P_(PL) is communicated to the pitchlock system 46 to counteract the coarse pitch pressure P_(c), balance the pitchlock piston 52 and maintain the pitchlock gap. The ballscrew screw 54 is mounted within the pitchlock nut 56 and the ballscrew ballnut 58 to rotationally advance or retreat over the full travel of the actuator yoke assembly 50 in response to movement of the pitch change actuator piston 49 through the differential pressure between the coarse pitch pressure P_(c) and the fine pitch pressure P_(F).

Referring to FIG. 4B, when the propeller system is commanded to pitchlock such as by a decrease in the coarse pitch pressure P_(c) which may result from a loss of hydraulic pressure, or by dumping of the pitchlock pressure P_(PL), the pitchlock system 46 is hydraulically initiated.

Once the hydraulic pressure on the pitchlock piston 52 is removed, the pitchlock piston 52 and pitchlock piston load tube 63 are biased (to the left in the figure) by a set of pitchlock springs 90. As the pitchlock piston load tube 63 strokes, the ballscrew bearing support assembly 62 (FIGS. 2A and 2B) which is mounted thereto also strokes to drive the pitchlock ballscrew screw 54 toward the axially fixed actuator dome cover 68 and close the pitchlock gap. The load from the pitchlock springs 90 loads the pitchlock ballscrew screw 54 against the axially fixed actuator dome cover 68. Contact with the axially fixed actuator dome cover 68 generates a torsional and an axial resistance which grounds the pitchlock ballscrew screw 54.

Referring to FIG. 4C, aerodynamic forces provide propeller blade loads which drives the pitch change system 48 and attached pitch change actuator piston 49 towards the fine pitch direction. The load driven through the ballscrew ballnut 58 and into pitchlock ballscrew screw 54 changes the contact angle (ie. direction) through the ball bearings 74. The load from piston springs 90 holds the pitchlock ballscrew screw 54 against the axially fixed actuator dome cover 68 while the bias from the pitch change actuator piston 49 being driven towards fine pitch results in a force which attempts to back-drive the pitchlock ballscrew screw 54. However, the resistant torsional friction loads between the ballscrew screw flange 66 and the fixed actuator dome cover 68 are greater than the torque which is attempting to back-drive through the pitchlock ballscrew screw 54 such that the ballscrew ballnut spring 78 begin to collapse (FIG. 4D).

Referring to FIG. 4D, the ballscrew ballnut spring 78 begins to collapse due to fine pitch load. The load from piston springs 90 maintains the pitchlock ballscrew screw 54 against the axially fixed actuator dome cover 68 while the bias from the pitch change actuator piston 49 being driven towards fine pitch attempts to back-drive the pitchlock ballscrew screw 54 and drive the ballscrew ballnut 58 therewith (note separation between the pitchlock nut 56 and the ballscrew ballnut 58). The pitch load continues to increase enough to further collapse the ballscrew ballnut spring 78 such that the ACME style pitchlock nut threads 86 contact the flanks of the continuous ballscrew ball track groove 64 until the lead angle results in a lock-up condition to thereby pitchlock the propeller system. Notably, no mechanical link is required between the rotating and non-rotating propeller components to initiate pitchlock.

When the pitchlock pressure P_(PL) is restored, the coarse pitch pressure P_(c) is balanced and the bias from the piston springs 90 is overcome such that the pitchlock piston 52, the pitchlock piston load tube 63, attached ballscrew bearing support assembly 62 and pitchlock ballscrew screw 54 returns to their normal operational position (FIG. 4A). Commensurate therewith, the ballscrew ballnut spring 78 repositions the ballnut 58 as the load on the ballscrew is removed such that the pitchlock gap returns (FIG. 4A) and normal operation again is available.

It should be understood that relative positional terms such as “forward,” “aft,” “upper,” “lower,” “above,” “below,” and the like are with reference to the normal operational attitude of the vehicle and should not be considered otherwise limiting.

It should be understood that although a particular component arrangement is disclosed in the illustrated embodiment, other arrangements will benefit from the instant invention.

Although particular step sequences are shown, described, and claimed, it should be understood that steps may be performed in any order, separated or combined unless otherwise indicated and will still benefit from the present invention.

The foregoing description is exemplary rather than defined by the limitations within. Many modifications and variations of the present invention are possible in light of the above teachings. The preferred embodiments of this invention have been disclosed, however, one of ordinary skill in the art would recognize that certain modifications would come within the scope of this invention. It is, therefore, to be understood that within the scope of the appended claims, the invention may be practiced otherwise than as specifically described. For that reason the following claims should be studied to determine the true scope and content of this invention. 

1. A pitchlock system comprising: a ballscrew screw mounted along an axis of rotation, said ballscrew screw having an external screw ball track groove; a pitchlock nut mounted about said ballscrew screw, said pitchlock nut including an internal pitchlock nut thread; a ballscrew ballnut mounted about said ballscrew screw and adjacent said ballscrew ballnut, said ballscrew ballnut having an internal ballnut track groove; and a ballscrew biasing member which biases said ballscrew ballnut toward said pitchlock nut, said ballscrew biasing member collapsible such that said ballscrew screw is movable between an operational position and a pitchlock position, said internal pitchlock nut thread lockable with said external screw ball track groove in said pitchlock position.
 2. The pitchlock system as recited in claim 1, wherein said internal ballnut track groove and said external screw ball track groove have a common helix angle.
 3. The pitchlock system as recited in claim 2, further comprising a multiple of ball bearings mounted within said internal ballnut track groove and said external screw ball track groove.
 4. The pitchlock system as recited in claim 1, wherein said pitchlock nut thread includes a toroidal profile, said pitchlock nut thread defines a clearance with said external screw ball track groove in said operation position.
 5. The pitchlock system as recited in claim 4, wherein said pitchlock nut thread includes a lead angle configured which prevents said ballscrew screw from back driving said pitchlock nut in said pitchlock position.
 6. The pitchlock system as recited in claim 4, wherein said pitchlock nut thread includes an ACME thread.
 7. The pitchlock system as recited in claim 4, wherein said pitchlock nut thread includes a screw thread profile which contacts only the flanks of the external screw ball track groove in said pitchlock position.
 8. The pitchlock system as recited in claim 1, further comprising a timing keyway between said pitchlock nut and said ballscrew ball nut to prevent rotation of said pitchlock nut and align said internal pitchlock nut thread and said internal ballnut track groove.
 9. The pitchlock system as recited in claim 1, wherein said ballscrew screw includes a flange engageable with a axially fixed surface to react a full actuator fine pitch hydraulic pressure output and a resultant blade load in response to said pitchlock position.
 10. The pitchlock system as recited in claim 1, further comprising a pitchlock piston having a pitchlock load tube, said ballscrew screw mounted for rotation about said pitchlock load tube through a ballscrew bearing support assembly.
 11. The pitchlock system as recited in claim 10, further comprising a pitchlock transfer tube mounted within said pitchlock load tube to communicate a pitchlock pressure to said pitchlock piston.
 12. A propulsor system comprising: a yoke assembly mounted along an axis of rotation, said yoke assembly defining a yoke bore; a ballscrew screw mounted along said axis of rotation and at least partially within said yoke bore, said ballscrew screw having an external screw ball track groove; a pitchlock nut mounted to said yoke bore and about said ballscrew screw, said pitchlock nut having an internal pitchlock nut thread; a ballscrew ballnut mounted for axial movement along said axis of rotation within said yoke bore adjacent said ballscrew ballnut and about said ballscrew screw, said ballscrew ballnut having an internal ballnut track groove; and a ballscrew biasing member within said yoke bore to axially bias said ballscrew ballnut toward said pitchlock nut, said ballscrew biasing member collapsible such that said ballscrew screw is movable between an operational position and a pitchlock position, said internal pitchlock nut thread lockable with said external screw ball track groove in said pitchlock position.
 13. The system as recited in claim 12, wherein said yoke assembly includes an actuator piston between a fine pitch chamber and a coarse pitch chamber, a multiple of blade assemblies mounted to said yoke assembly.
 14. The system as recited in claim 13, wherein said ballscrew screw includes a flange engageable with a axially fixed surface of said coarse pitch chamber to react a full actuator fine pitch hydraulic pressure output and a resultant aerodynamic blade load in response to said pitchlock position.
 15. The system as recited in claim 14, further comprising a pitchlock piston adjacent said axially fixed surface opposite said flange, said pitchlock piston in contact with a pitchlock load tube which extends through said axially fixed surface, said ballscrew screw mounted for rotation about said pitchlock load tube through a ballscrew screw support assembly.
 16. The pitchlock system as recited in claim 15, further comprising a pitchlock transfer tube mounted within said pitchlock load tube to communicate a pitchlock pressure to said pitchlock piston, said pitchlock pressure in opposition to a coarse pitch pressure within said coarse pitch chamber.
 17. A method of pitchlocking a propulsor system comprising the steps of: (1) axially biasing a ballscrew ballnut toward a pitchlock nut, the ballscrew ballnut and pitchlock nut rotationally fixed relative a ballscrew screw mounted for backdriving therein; (2) overcoming the biasing of said step (1) in response to a pitchlock condition; and (3) axially shifting the ballscrew screw such that an external ball track groove of the ballscrew screw engages with a set of internal pitchlock nut threads and the ballscrew screw is prevented from backdriving within the pitchlock nut.
 18. A method as recited in claim 17, wherein said step (2) further comprises: changing a contact angle between a set of ball bearings between the ballscrew ballnut and the ballscrew screw.
 19. A method as recited in claim 17, wherein said step (2) further comprises: axially loading the ballscrew ballnut in a fine pitch direction until the axially load overcomes the biasing.
 20. A method as recited in claim 17, wherein said step (3) further comprises the steps of: (a) axially shifting the ballscrew screw in response to a reduction of coarse pitch pressure below a predetermined blade load; and (b) closing a pitchlock gap between the ballscrew screw and contact surface such that the ballscrew screw contacts the contact surface such that the ballscrew is prevented from rotating. 